Phase II Final Report - NASA's Institute for Advanced Concepts

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars The wing planform provided by GTRI to Metacomp Technologies for conversion to a CFD mesh included a "blown flap" with a radius that was 4% of the maximum chord value as shown in Figure 3-82. For the 0.6m winglet span, the max chord of the blown part is about 0.2m. This leads to a 4% radius of about 8mm. Due to various constraints the blowing slot, tangential to the blown flaps at the outer trailing edge and wing tip, was simulated to be about twice as large as it would be were it to be implemented physically. This could result in a higher mass flow than necessary to achieve a given degree of pneumatic control. Figure 3-82: Dimensions Used for Entomopter Wing Mesh Generation The Entomopter wing is designed to change its angle of attack at the top and bottom of the flapping cycle based on the compliance of the wing material so that an optimum angle of attack (α) is achieved without the use of actuators. The wing angle of attack changes throughout each wing beat due to the absolute velocity change of each point along the wing as well as the flexing motion of the wing itself. For the purposes of the Metacomp Technologies CFD wing design, this change of wing α occurs rapidly near the top and bottom of the flap (rather than continuously). Specifically, the angle of attack was chosen to be -8 o for the down beat, and +8 o for the upbeat. Since most of the lift is expected to come from the wing beating and not the forward flight, the wing makes its flip from –8 o to +8 o (and vice versa) in the first 10 o of wing flapping after reaching the maximum excursion at the top/bottom of the flap. The rate of change in the angle is modeled to be linear over this 10 o (going from –8 o to +8 o and vice versa) with the ±8 o being held constant over the remainder of the flap. Input parameters and boundary conditions used in this CFD analysis were: 1. Mars atmospheric parameters (STP within 3m of Mars equatorial surface) 2. Altitude: near surface (under 3m above mean planetary ground level) 98 Phase II Final Report
3. Density: 1.40E-2 kg/m 3 4. Pressure: 750 Pa 5. Temperature: 263° K 6. Speed of sound: 265 m/s 7. Viscosity: 1.35E-5 kg/m s 8. Kinematic viscosity: 9.65E-4 m 2 /s 9. Flapping frequency: 6 Hz 10. Inflow (forward flight) speed: 14 m/s 11. Wing flapping angle: ±75 degrees from horizontal Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics 3.3.1.5.1 Mesh Topology In the earlier computational studies, which focused on the flapping motion, Metacomp Technologies had used a relatively crude mesh. Also, they had not included the full details of the geometry of the blown flap. Subsequent studies modeled the blown flap region geometry, and developed a more dense mesh. On this mesh, Metacomp Technologies first studied the non-flapping case, with and without blowing. This section describes the overall mesh system topology. In the following, “x” is the freestream direction, “y” is the vertical and “z” is the spanwise direction. The wing extends along the negative z direction. Figures 3-83 through 3-88 present several views of the mesh used. For the simulations with blowing, the mesh has been further refined in the blown flap region. But the overall topology is similar to the figures shown below. Figure 3-83: Mesh View 1 99
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Planetary Exploration Using Biomime
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Table of Contents Table of Contents
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List of Tables List of Tables Table
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List of Figures List of Figures Fig
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List of Figures Figure 3-54: Pressu
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List of Figures Figure 3-138: Stere
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List of Figures Figure 4-24: Averag
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List of Contributors List of Contri
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Executive Summary Executive Summary
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Chapter 1.0 Introduction Chapter 1.
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Chapter 1.0 Introduction Figure 1-2
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Chapter 1.0 Introduction 1.1 Histor
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Chapter 1.0 Introduction 1.2 Origin
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Chapter 1.0 Introduction 1.3 Missio
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1.3.3.1 Surface Imaging The Entomop
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Chapter 2.0 Entomopter Configuratio
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Chapter 3.0 Vehicle Design 3.1 Wing
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Chapter 3.0 Vehicle Design 3.4 Reci
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Chapter 3.0 Vehicle Design 3.5 Fuel
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Chapter 3.0 Vehicle Design 3.6 Powe
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Chapter 4.0 Entomopter Flight Opera
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Chapter 5.0 Potential Payload Funct
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Chapter 6.0 Media Exposure 6.1 Intr
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Chapter 6.0 Media Exposure 6.3 Onli
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Chapter 6.0 Media Exposure 6.6 Spec
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Chapter 7.0 Conclusion Chapter 7.0
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Appendix A: Mars Atmosphere Data JP
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ma
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Appendix B: Sizing Results Appendix
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Appendix B: Sizing Results 30 Wing
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Appendix B: Sizing Results 16 Wing
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Appendix B: Sizing Results Length 0
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Appendix B: Sizing Results Lenght 0
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Appendix C: List of References Appe
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Appendix C: List of References 41.
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Phase II Final Report - NASA's Institute for Advanced Concepts

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